Patents by Inventor Edwin Otero

Edwin Otero has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20230296028
    Abstract: A method of damping vibrations in a seal includes inserting a first wave spring between a first beam and a second beam of the seal. The seal can be for a gas turbine engine and can include a full hoop outer ring, a shoe coupled to the full hoop outer ring via the first beam (e.g., an outer beam) and the second beam (e.g., an inner beam), and the first wave spring in contact with the first beam and the second beam.
    Type: Application
    Filed: May 3, 2023
    Publication date: September 21, 2023
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, John R. Farris, Michael G. McCaffrey, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
  • Patent number: 11674401
    Abstract: A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.
    Type: Grant
    Filed: May 13, 2020
    Date of Patent: June 13, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Ross Wilson, John R. Farris, Michael G. McCaffrey, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
  • Patent number: 11306619
    Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
    Type: Grant
    Filed: June 27, 2019
    Date of Patent: April 19, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
  • Patent number: 11287045
    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.
    Type: Grant
    Filed: January 9, 2019
    Date of Patent: March 29, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Ross Wilson, Edwin Otero, Alan W. Stoner
  • Patent number: 11261737
    Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.
    Type: Grant
    Filed: January 15, 2018
    Date of Patent: March 1, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Daniel A. Snyder, Edwin Otero, Di Wu, Timothy Charles Nash, Brandon W. Spangler
  • Patent number: 10975705
    Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.
    Type: Grant
    Filed: October 22, 2019
    Date of Patent: April 13, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Edwin Otero
  • Patent number: 10907482
    Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour.
    Type: Grant
    Filed: September 10, 2018
    Date of Patent: February 2, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel A. Snyder, Jaimie Schweitzer, Jonathan Perry Sandoval, Edwin Otero, Kyle C. Lana, Scott D. Virkler
  • Patent number: 10801348
    Abstract: Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam.
    Type: Grant
    Filed: September 14, 2015
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Ross Wilson, John R. Farris, Michael G. McCaffrey, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
  • Publication number: 20200271006
    Abstract: A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.
    Type: Application
    Filed: May 13, 2020
    Publication date: August 27, 2020
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, John R. Farris, Michael G. McCaffrey, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
  • Publication number: 20200149413
    Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.
    Type: Application
    Filed: October 22, 2019
    Publication date: May 14, 2020
    Inventors: Brandon W. Spangler, Edwin Otero
  • Patent number: 10641129
    Abstract: A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: May 5, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Jose R. Paulino, Craig R. McGarrah, Edward R. Bareiss, Edwin Otero
  • Patent number: 10557354
    Abstract: A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: February 11, 2020
    Assignee: United Technologies Corporation
    Inventors: Edwin Otero, Kyle C. Lana
  • Publication number: 20200025293
    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.
    Type: Application
    Filed: January 9, 2019
    Publication date: January 23, 2020
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Ross Wilson, Edwin Otero, Alan W. Stoner
  • Patent number: 10487668
    Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.
    Type: Grant
    Filed: August 27, 2014
    Date of Patent: November 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Edwin Otero
  • Publication number: 20190331003
    Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
    Type: Application
    Filed: June 27, 2019
    Publication date: October 31, 2019
    Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
  • Patent number: 10443450
    Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
  • Patent number: 10436051
    Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: October 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
  • Patent number: 10399189
    Abstract: A method of manufacturing an airfoil. The method includes fixing the airfoil in a workpiece space, detecting a position of the airfoil in the workpiece space using a force-sensing element, and removing material from the airfoil to reduce a dimension of the airfoil. In various embodiments, detecting the position of the airfoil includes moving the force-sensing element across a surface of the airfoil. For example, the surface of the airfoil may be a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface. Removing material from the second surface of the airfoil may be performed without moving the force-sensing element across the second surface of the airfoil.
    Type: Grant
    Filed: October 10, 2016
    Date of Patent: September 3, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eric A. Hudson, Alan C. Barron, Edwin Otero
  • Patent number: 10378364
    Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
    Type: Grant
    Filed: November 7, 2017
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Edwin Otero, David R. Pack
  • Patent number: 10370991
    Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.
    Type: Grant
    Filed: August 19, 2015
    Date of Patent: August 6, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Michael G McCaffrey, John R Farris, Theodore W Hall, John J Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, Edwin Otero, John E Paul